Turbine engine airfoil

Abstract

An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.

What is claimed is: 
     
       1. An airfoil for a turbine engine, comprising:
 an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction; 
 a plurality of outlets on the trailing edge; and 
 a cooling passage within the interior and comprising:
 a first portion extending along a first direction; 
 a second portion fluidly coupled to, and downstream of, the first portion, the second portion extending along a second direction at least partially opposite the first direction; and 
 a third portion downstream of the second portion, the third portion comprising an inlet passage fluidly coupled to the second portion and a plurality of outlet passages fluidly coupled to the plurality of outlets. 
 
 
     
     
       2. The airfoil of  claim 1 , wherein both of the first direction and the second direction are at least partially aligned with one of the span-wise direction or the chord-wise direction. 
     
     
       3. The airfoil of  claim 1 , further comprising a fourth portion coupling the first portion to the second portion. 
     
     
       4. The airfoil of  claim 3 , wherein the fourth portion extends along a fourth direction unaligned with the first direction and the second direction. 
     
     
       5. The airfoil of  claim 3 , wherein the fourth portion fluidly couples the first portion to the second portion. 
     
     
       6. The airfoil of  claim 1 , wherein the first portion defines a first passage width and the second portion defines a second passage width, wherein the second passage width is the same size or smaller than the first passage width. 
     
     
       7. The airfoil of  claim 1 , wherein the cooling passage at least partially defines a three-dimensional plexus of fluidly interconnected cooling passages. 
     
     
       8. The airfoil of  claim 1 , wherein the plurality of outlets are arranged at least partially along the span-wise direction. 
     
     
       9. The airfoil of  claim 1 , wherein the plurality of outlets are proximate the trailing edge. 
     
     
       10. The airfoil of  claim 1 , wherein the third portion furcates at least twice along a downstream direction toward the plurality of outlets. 
     
     
       11. An airfoil for a turbine engine, comprising:
 an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction; 
 a plurality of outlets on the trailing edge; and 
 a cooling passage within the interior and comprising:
 a serpentine portion having at least one passage turn; and 
 a furcated portion having an inlet passage fluidly coupled to the serpentine portion and a plurality of outlet passages fluidly coupled to the plurality of outlets. 
 
 
     
     
       12. The airfoil of  claim 11 , wherein the serpentine portion comprises a first portion and a second portion, with the passage turn fluidly coupling the first portion and the second portion. 
     
     
       13. The airfoil of  claim 12 , wherein the first portion extends along a first direction and the second portion extends along a second direction at least partially opposite the first direction. 
     
     
       14. The airfoil of  claim 13 , wherein both of the first direction and the second direction are at least partially aligned with one of the span-wise direction or the chord-wise direction. 
     
     
       15. The airfoil of  claim 12 , further comprising an additional portion in the serpentine portion forming an additional fluid coupling between the first portion and the second portion. 
     
     
       16. The airfoil of  claim 12 , wherein the first portion defines a first passage width and the second portion defines a second passage width, wherein the second passage width is the same size or smaller than the first passage width. 
     
     
       17. The airfoil of  claim 11 , wherein the cooling passage at least partially defines a three-dimensional plexus of fluidly interconnected cooling passages. 
     
     
       18. The airfoil of  claim 11 , wherein the plurality of outlet passages in the furcated portion are arranged at least partially along the span-wise direction. 
     
     
       19. The airfoil of  claim 11 , wherein the plurality of outlets are proximate the trailing edge. 
     
     
       20. The airfoil of  claim 11 , wherein the furcated portion furcates at least twice along a downstream direction toward the plurality of outlets.